Hostname: page-component-78c5997874-m6dg7 Total loading time: 0 Render date: 2024-11-09T05:39:09.168Z Has data issue: false hasContentIssue false
  • English
  • Français

The Effects of Recessed Lower Surface Shape on the Lift and Drag of Conical Wings at High Incidence and High Mach Number

Published online by Cambridge University Press:  07 June 2016

L C Squire
L C Squire*
Affiliation:
Cambridge University Engineering Department
Get access

Summary

For lifting re-entry there may be advantages in using wings which give as high a lift coefficient as possible at the design value of the lift/drag ratio. This paper presents the results of an experimental and theoretical study of wings with recessed lower surfaces designed to give high values of CL. The calculations show that a wide range of wing shapes can be found that give values of CL which are much larger than those on a flat wing with the same lift/drag ratio.

Type
Research Article
Information
Aeronautical Quarterly , Volume 26 , Issue 1 , February 1975 , pp. 1 - 10
Copyright
Copyright © Royal Aeronautical Society. 1975

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1 Townend, L H Some design aspects of space shuttle orbiters. Progress in Aerospace Sciences, Vol 13, pp 81–136, Pergamon, 1972.Google Scholar
2 Squire, L C A comparison of the lift of flat delta wings and waveriders at high angles of incidence and high Mach number. Ingenieur-Archiv, Vol 40, pp 339–352, 1971.Google Scholar
3 Shanbhag, V V Numerical studies on hypersonic delta wings with detached shock waves. ARC Current Paper 1277, 1974.Google Scholar
4 Squire, L C Some extensions of thin-shock-layer theory. Aeronautical Quarterly, Vol XXV, pp 1–13, February 1974.Google Scholar
5 Bazzhin, A P Calculation of the flow past plane triangular wings at large angles of attack. Iz AN SSSR Mekhanika Zhidkosti i Gaza, Vol 2, pp 119–123, 1967.Google Scholar
6 Bashkin, V A Experimental study of flow about flat delta wings at M = 5 and angles of attack from 0 to 70°. Izv AN SSSR Mekhanika Zhidkosti i Gaza, Vol 2, pp 102–108, 1967.Google Scholar